[Federal Register Volume 69, Number 216 (Tuesday, November 9, 2004)]
[Rules and Regulations]
[Pages 64832-64834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-24717]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18579; Directorate Identifier 2004-CE-19-AD; 
Amendment 39-13856; AD 2004-23-01]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes with any Lear 
Romec RR53710B type or Lear Romec RR53710K fuel booster pump (Pilatus 
part number 968.84.11.401; 968.84.11.403; or 968.84.11.404) installed. 
This AD requires you to check the airplane logbook to determine whether 
any installed fuel booster pump has been modified with spiral wrap to 
protect the wire leads and has the suffix letter ``B'' added to the 
serial number of the fuel booster pump identification plate. If any 
installed fuel booster pump has not been modified, you are required to 
inspect any installed fuel booster pump wire lead for defects; if 
defects are found, replace the fuel booster pump with a modified fuel 
booster pump with spiral wrap that protects the wire leads; or if no 
defects are found, install spiral wrap to protect any wire leads and 
add the suffix letter ``B'' to the serial number of the fuel booster 
pump identification plate. The pilot is allowed to do the logbook 
check. If the pilot can positively determine that the fuel booster pump 
wire leads with spiral wrap are installed following the service 
information and that the suffix letter ``B'' is included in the serial 
number of the fuel booster pump identification plate, no further action 
is required. This AD is the result of mandatory continuing 
airworthiness information (MCAI) issued by the airworthiness authority 
for Switzerland. We are issuing this AD to detect and correct any 
defects in the leads of any fuel booster pump, which could result in 
electrical arcing. This failure could lead to a fire or explosion in 
the fuel tank.

DATES: This AD becomes effective on December 27, 2004.
    As of December 27, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-
mail: aircraft.com">SupportPC12@pilaltus-aircraft.com or from Pilatus Business 
Aircraft Ltd., Product Support Department, 11755 Airport Way, 
Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303) 
465-6040. To review this service information, go to the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or 
call (202) 741-6030.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-18579.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this AD? The Federal Office for Civil 
Aviation (FOCA), which is the airworthiness authority for Switzerland, 
recently notified FAA that an unsafe condition may exist on certain 
Pilatus Model PC-7 airplanes. The FOCA reports that there have been 11 
reports of damaged fuel boost pump wire leads from 9 Model PC-12 
airplanes that have a similar type design. Further, the FOCA reports 
that it is possible that the wire leads to the left and right fuel 
pumps are damaged. This could possibly cause electrical arcs from the 
leads in an air/fuel mixture.
    What is the potential impact if FAA took no action? Any electrical 
arcing could lead to a fire or explosion in the fuel tank.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to certain Pilatus Model PC-7 airplanes 
with any Lear Romec RR53710B type or Lear Romec RR53710K fuel booster 
pump (Pilatus part number 968.84.11.401; 968.84.11.403; or 
968.84.11.404) installed. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on August 20, 2004 
(69 FR 516161). The NPRM proposed to require you to check the airplane 
logbook to determine whether any installed fuel booster pump has been 
modified with spiral wrap to protect the wire leads and has the suffix 
letter ``B'' added to the serial number of the fuel booster pump 
identification plate. If any installed fuel booster pump has not been 
modified, you are required to inspect any installed fuel booster pump 
wire lead for defects; if defects are found, replace the fuel booster 
pump with a modified fuel booster pump with spiral wrap that protects 
the wire leads; or if no defects are found, install spiral wrap to 
protect any wire leads and add the suffix letter ``B'' to the serial 
number of the fuel booster pump identification plate. The pilot is 
allowed to do the logbook check. If the pilot can positively determine 
that the fuel booster pump wire leads with spiral wrap are installed 
following the service information and that the suffix letter ``B'' is 
included in the serial number of the fuel booster pump identification 
plate, no further action is required.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

--Are consistent with the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

[[Page 64833]]

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 10 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to do the 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                               Total cost  per
             Labor cost                      Parts cost            airplane       Total cost  on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.....  Not applicable.........             $65   $65 x 10 = $650.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacement of 
any fuel boost pump, including the installation of any wire wrap, that 
will be required based on the results of the inspection. We have no way 
of determining the number of airplanes that may need this installation:

------------------------------------------------------------------------
                                                       Total cost per
         Labor cost                Parts cost             airplane
------------------------------------------------------------------------
5 workhours x $65 per hour =  $2,800 for each fuel  $2,800 x $325 =
 $325.                         booster pump.         $3,125 for each
                                                     fuel booster pump
                                                     installation.
------------------------------------------------------------------------

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD will not have a substantial direct effect on the States, on the 
relationship between the national government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``Docket No. FAA-2004-18579; Directorate Identifier 2004-CE-19-AD'' in 
your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2004-23-01 Pilatus Aircraft Ltd.: Amendment 39-13856; Docket No. 
FAA-2004-18579; Directorate Identifier 2004-CE-19-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on December 27, 2004.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model PC-7 airplanes, serial numbers 101 
through 618, that are:
    (1) equipped with Lear Romec RR53710B type or Lear Romec 
RR53710K fuel booster pump, Pilatus part number (P/N) 968.84.11.401; 
968.84.11.403; or 968.84.11.404; and
    (2) certificated in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland. The actions specified in this AD are intended to detect 
and correct any defects in the leads of any fuel booster pump, which 
could result in electrical arcing. This failure could lead to a fire 
or explosion in the fuel tank.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Check the airplane        Within 50 hours time- The owner/operator
 logbook to to ensure that     in-service (TIS)      holding at least a
 any fuel booster pump (part   after December 27,    private pilot
 number (P/N) 968.84.11.401;   2004 (the effective   certificate as
 968.84.11.403; or             date of this AD),     authorized by
 968.84.11.404) has been       unless already done.  section 43.7 of the
 modified with spiral wrap                           Federal Aviation
 to protect the wire leads                           Regulations (14 CFR
 and has the suffix letter                           43.7) may perform
 ``B'' added to the serial                           this check.
 number of the fuel booster
 pump identification plate
 as required by paragraph
 (e)(5) of this AD.
-----------------------------

[[Page 64834]]

 
(2) If you can positively     Not Applicable......  Make logbook entry.
 determine that any fuel
 booster pump (P/N
 968.84.11.401;
 968.84.11.403; or
 968.84.11.404) has been
 modified following the
 Accomplishment
 Instructions--Aircraft
 section in Pilatus PC-7
 Service Bulletin No. 28-
 009, dated October 6, 2003,
 and has the suffix letter
 ``B'' added to the serial
 number of the fuel booster
 pump identification plate
 as required by paragraph
 (e)(5) of this AD, then no
 further action is required.
-----------------------------
(3) Inspect any fuel booster  Within 50 hours TIS   Follow the
 pump (P/N 968.84.11.401;      after December 27,    Accomplishment
 968.84.11.403; or             2004 (the effective   Instructions--Aircr
 968.84.11.404) leads for      date of this AD),     aft section in
 any defects.                  unless already done.  Pilatus PC-7
                                                     Service Bulletin
                                                     No. 28-009, dated
                                                     October 6, 2003.
                                                     This subject is
                                                     also addressed in
                                                     the Pilatus PC-7
                                                     Airplane
                                                     Maintenance Manual.
-----------------------------
(4) If any defect is found    Before further        Follow the
 during the inspection         flight after the      Accomplishment
 required by paragraph         inspection required   Instructions--Aircr
 (e)(3) of this AD, replace    by paragraph (e)(3)   aft section in
 the fuel booster pump.        of this AD in which   Pilatus PC-7
                               any defect is found.  Service Bulletin
                                                     No. 28-009, dated
                                                     October 6, 2003.
                                                     This subject is
                                                     also addressed in
                                                     the Pilatus PC-7
                                                     Airplane
                                                     Maintenance Manual.
-----------------------------
(5) If no defects are found   Before further        Follow the
 during the inspection         flight after the      Accomplishment
 required by paragraph         inspection required   Instructions--Aircr
 (e)(3) of this AD, modify     by paragraph (e)(3)   aft section in
 any fuel booster pump (P/N    of this AD where no   Pilatus PC-7
 968.84.11.401;                defect is found.      Service Bulletin
 968.84.11.403; or                                   No. 28-009, dated
 968.84.11.404) by                                   October 6, 2003.
 installing the lead                                 This subject is
 inspection by using a                               also addressed in
 spiral wrap. After doing                            the Pilatus PC-7
 the modification, re-                               Airplane
 identify the fuel booster                           Maintenance Manual.
 pump (P/N 968.84.11.401;
 968.84.11.403; or
 968.84.11.404) by adding
 the suffix letter ``B'' to
 the serial number of the
 fuel booster pump
 identification plate.
-----------------------------
(6) Do not install any fuel   As of December 27,    Follow the
 booster pump (P/N             2004 (the effective   Accomplishment
 968.84.11.401;                date of this AD).     Instructions--Spare
 968.84.11.403; or                                   s section in
 968.84.11.404) that has not                         Pilatus PC-7
 been modified and                                   Service Bulletin
 identified with the suffix                          No. 28-009, dated
 letter ``B'' to the serial                          October 6, 2003.
 number of the fuel booster
 pump identification plate.
------------------------------------------------------------------------

    Note 1: The FAA recommends that you incorporate Pilatus PC-7 
Maintenance Manual No. 28-20-03, dated November 30, 2003, and 
Pilatus PC-7 Maintenance Manual No. 12-10-01, dated November 30, 
2003, in the appropriate section of the airplane maintenance manual.
    Note 2: Wiring defects are addressed in paragraph 11-97 in FAA 
Advisory Circular (AC) 43.13-1B.

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, contact Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090.

Is There Other Information That Relates to This Subject?

    (g) Swiss AD Number HB-2004-210, issue dated June 11, 2004, also 
addresses the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in Pilatus PC-7 Service Bulletin No. 28-009, dated 
October 6, 2003. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this 
service information, contact Pilatus Aircraft Ltd., Customer Liaison 
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208; 
facsimile: +41 41 619 7311; e-mail: aircraft.com">SupportPC12@pilaltus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support 
Department, 11755 Airport Way, Broomfield, Colorado 80021; 
telephone: (303) 465-9099; facsimile: (303) 465-6040. To review 
copies of this service information, go to the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call 
(202) 741-6030. To view the AD docket, go to the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on 
the Internet at http://dms.dot.gov. The docket number is FAA-2004-
18579.

    Issued in Kansas City, Missouri, on October 29, 2004.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-24717 Filed 11-8-04; 8:45 am]
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